US3398916A - Device for correcting the trajectory of projectiles and the so-equipped projectiles - Google Patents

Device for correcting the trajectory of projectiles and the so-equipped projectiles Download PDF

Info

Publication number
US3398916A
US3398916A US64689967A US3398916A US 3398916 A US3398916 A US 3398916A US 64689967 A US64689967 A US 64689967A US 3398916 A US3398916 A US 3398916A
Authority
US
Grant status
Grant
Patent type
Prior art keywords
projectile
trajectory
projectiles
device
correcting
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
Inventor
Frederic Edouard Antoine Vyve
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
FN Herstal SA
Original Assignee
FN Herstal SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Grant date

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/222Homing guidance systems for spin-stabilized missiles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30Command link guidance systems
    • F41G7/301Details
    • F41G7/305Details for spin-stabilized missiles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60Steering arrangements
    • F42B10/66Steering by varying intensity or direction of thrust
    • F42B10/661Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge

Description

A 27, 1968 F. E. A. VAN VYVE 3,398,916

DEVICE FOR CORRECTING THE TRAJECTORY OF PROJECTILES AND THE SO-EQUIPPED PROJECTILES Filed June 19, 1967 FRFDERIC EDWARD ANWINE VAN V) VF INVENTOR. W .L 6g,

A 'MRNEYS United States Patent 3,398,916 DEVICE FOR CORRECTING THE TRAJECTORY 0F PROJECTILES AND THE SO-EQUIPPED PROJECTILES Frederic Edouard Antoine Van Vyve, Viveguis, Belgium, assignor to Fabrique Nationale dArmes de Guerre Societe Anouyme, Herstal-lez-Liege, Belgium Filed June 19, 1967, Ser. No. 646,899 Claims priority, appligation Belgium, July 4, 1966,

2 Claims. cl. 244-311 ABSTRACT OF THE DISCLOSURE A trajectory correcting device including an auxiliary projectile for a projectile rotating about its longitudinal axis along the trajectory thereof and comprising a remotely controllable detecting device.

Background of the invention This invention relates to projectiles of the type comprising a remotely controllable detecting device, said projectile being rotated along its trajectory by its own characteristics or those of its launching means.

The detecting device may be of any suitable type remotely controllable either by electromagnetic waves or by waves emitted from a source of coherent luminous waves (laser) or by infrared waves, e.g. those emitted by a motor exhaust and the like.

These waves may be emitted or reflected by the target or the shooter and generally they may reach the detecting device in any suitable manner.

The object of the present invention is to cause the suitable intervening of a substantial lateral thrust capable of modifying almost instantaneously the trajectory of the projectile to bring it on the target.

One of the major difiiculties encountered heretofore results from the importance of the amplitude of the angular correction being brought to the trajectory of the projectile to ensure a favorable probability of reaching the target within a very large variety of shooting conditions.

It has already been proposed to provide the projectiles with a'lateral thrust device expelling at due time and in the intended direction a mass of gases the ejection of which causes a rapid modification of the projectile slant, thereby resulting in a modification of the trajectory.

However, this solution is precarious 'due to, on one hand, the small value of the gas mass expelled with respect to the projectile mass and consequently the relatively small value of the resulting force system and, on the other hand, the way of applying said force. In fact, it is observed that this lateral is applied in such manner that it results only in a torque causing the projectile to slant by rotating about its center of gravity, the resulting slant modifying progressively the trajectory owing to the aerodynamic characteristics of the projectile. Accordingly, the modification of the trajectory requires a relatively long time and the angular value of this modification may not be obtained with a suflicient accuracy.

In addition, in such known devices, the pivoting speed of the projectile about its center of gravity owing to the ejection of the gas mass must be brought back to Zero by another force, thereby giving rise to an additional inaccuracy of the angular correction of the projectile trajectory and a substantial complication of the construction and the operation thereof.

It is an object of the present invention to provide a trajectory correcting device, more particularly for projectiles of the above mentioned type, with which the 3,398,916 Patented Aug. 27, 1968 drawbacks of the known devices are systematically avoided.

Another object of the invention is to make such device from a minimum number of constituting elements readily assembled, thereby allowing to reach relatively low cost prices with respect to the performances of the projectile.

Still another object of the invention relates to a particular construction of such device offering a great resistance to lateral stresses when correcting the trajectory.

Summary of the invention The correcting device according to the invention is characterized in that it comprises a make-up charge and an auxiliary projectile arranged in such manner that the resultant of the reaction forces created by the ejection of said auxiliary projectile is lateral, passes through or at close vicinity to the center of gravity of the projectile and is such that it may induce almost instantaneously a correction of the trajectory to bring the projectile on the target.

Thus, the new trajectory of the main projectile is determined by the resultant of two orthogonal linear movements the first of which is caused by the propelling force of the main projectile, while the second movement results from the propelling force of the auxiliary projectile passing through or at close vicinity to the center of gravity of the said main projectile.

It is apparent that said auxiliary projectile will be injeoted substantially at the time of the detection and said time itself will correspond to such an angular position of the projectile that the speed vector of the auxiliary projectile is situated within or approximately within a plane including both the target and the longitudinal axis of the main projectile.

It will be observed that the speed vector of the auxiliary projectile may be also situated within a plane slightly diiferent from that just described above to take account of surrounding factors such as, for instance, the time necessary for ejecting the auxiliary projectile, the shifting of the target and the like.

It is important that the speed of the projectile remains constant along its trajectory. For this purpose, the projectile provided with the device according to the invention will be correlatively conditioned by any suitable means providing for such constant speed. In a preferred embodiment of the invention, the projectile will be provided with a flight motor to define accurately the angular amplitude of the trajectory correction resulting from the combination of said speed with the transverse speed imparted by the lateral thrust.

The flight motor will be such that the thrust with which it actuates the projectile, is approximately equal to the resistance to the advance of the projectile relatively to its initial speed.

Without limitation, an example of trajectory correcting device for a projectile and a so equipped projectile will be described hereafter in their essential elements with reference to the enclosed drawings wherein:

FIGURE 1 shows very diagrammatically a longitudinal section of a projectile and the correcting device according to the invention;

FIGURE 2 shows a section taken on the line IIII of FIGURE 1;

FIGURE 3 shows diagrammatically the correcting process resulting from the device and the projectile according to the invention.

Description of the preferred embodiment 3 into two chambers 6-7 by a cross-piece 8 the longitudinal axis A-A of which is at right angles or substantially at right angles to the longitudinal axis BB of the projectile.

In that case, the chamber 6 houses the charge, generally a hollow charge represented at 9. Chamber 7 houses a suitable device providing for the flight speed of the projectile. In the selected embodiment, this device comprises a flight motor represented in 10. The cross-piece 8 has a blind hole 11 the longitudinal axis of which merges with the said axis A-A.

Said blind hole houses at least a priming element or device 12, a charge 13, an auxiliary projectile, namely a plug 14 and a lid 15.

The highly resistant body is preferably reinforced by any suitable means in the plane of the lateral thrust.

In this respect and, in a particular embodiment, the tubular element will have an increasing thickness from its ends or at a distance from its ends 1617 and in the direction of the cross-piece 8. Similarly, the bottom of the said blind hole 11 will be conditioned or shaped to present a great resistance. W

The head 3 will comprise a detecting device 18 which will be selected in accordance with the used detecting way, i.e. the nature of the waves of the emitter.

Heretofore, there are known a number of such detecting devices likely to be remotely controlled, even at an important distance, by magnetic, heat and light waves and the like.

The head 3 will be generally provided with a conventional protecting cap 19 having a spherical, ogival or similar shape. According to conditions, a transparent or opaque material will be selected but, in any case, said material will be permeable to the waves having to reach or operate the detecting device represented in 18.

Generally, use will be advantageously made of plastic materials which are well known at the present and which are also used for similar purposes.

The fins 4 will be also shaped and conditioned in any suitable manner.

The detecting device or the projectile provided therewith will operate substantially as follows: the projectile 1 is brought as accurately as possible to bear on a point adjacent to the target. At a point of the trajectory of the projectile 1, the detecting device 18 is remotely energized by a known means, e.g. by directing directly a train or a beam of waves thereto or by reflecting said waves, e.g. from the target or in any other manner. At that time, as diagrammatically represented in FIGURE 3, the projectile 1 is subjected simultaneously to the flight speed before the lateral thrust represented by the vector V1 and at a complementary speed indicated by vector W2 and resulting from the relative speed of the auxiliary projectile 14 indicated by vector W1. Accordingly, the projectile 1 is then subjected to a resulting speed indicated by vector V2 which must be tangential to a trajectory represented in t passing through the target 0 or at close vicinity of the latter.

For that purpose, it will be noted that the detecting device 18 will be necessarily energized, i.e. that also the charge 13 for propelling the auxiliary projectile 14 will be fired when the vector W1 representing the speed of the auxiliary projectile lies within or approximately within a plane including both the longitudinal axis BB of the projectile 1 and the target 0.

It Will be apparent that the tolerances are directly depending upon the shooting conditions and that the auxiliary charge 13 could be also fired for any other relative position of said vector W1 so that the projectile impacts against the target or at close vicinity thereof.

It will be noted that, with relatively simple measures, the projectile according to the invention provides a very great shooting accuracy. In fact, the principal parameters having an influence upon the precision may be predetermined with sufficient accuracy, provided of course that the launching arm has been correctly aimed. In fact, the angle at which the detecting device 8 may see the target is known and the value of said angle makes possible to a determination of the angular value of the correction being given to the trajectory of the projectile, the speed of the latter being constant and known. The value of this correction may be reproduced with sufiicient accuracy since the resultant of the reaction forces acting upon the center of gravity G of the projectile at the time of the ejection of the auxiliary projectile is known within sufiicient limits, said center of gravity G being shifted in a very short time. It is also to be noted that the thrust of the flight motor is selected to be equal or practically equal to the resistance to advance of the projectile relatively to its initial speed. Of course, this makes it possible to maintain the angle of lateral correction (angle of lateral thrust) constant for every flight state.

It is apparent that the characteristics of this invention will be worked under essentially varying forms in accordance with the means adapted for the detection under the particular conditions disclosed herein to induce the lateral thrust so that the projectile will be maintained in rotation at a reduced speed about its axis and the like. Generally, the projectile will be provided with a single charge and auxiliary projectile. It is apparent that, in particular cases, two or more charges and make-up projectiles could be applied provided that they meet the operating requirements disclosed herein.

In brief, this invention covers any detection projectile using the foregoing characteristics as well as the projectile parts specially conditioned therefor.

What I claim is:

1. A projectile, comprising an elongated tubular body, a hollow head carried by one end of said body, a detecting device within said head, a central cross piece located within said body between the ends thereof and dividing the interior of the body into a front chamber and a rear chamber, said cross piece having a blind hole the longitudinal axis of which extends at right angles to the longitudinal axis of said body, a charge within said front chamber, a flight motor within said rear chamber for maintaining constant the speed of the projectile, a priming element in said hole, an auxiliary charge in said hole controlled by said detecting device, and an auxiliary projectile in said hole substantially in the center of gravity of the projectile, whereby resultant reaction forces caused by the lateral ejection of said auxiliary projectile pass through said center of gravity.

2. A projectile according to claim 1, wherein the tubular body has an increasing thickness from its ends and in the direction of the central cross-piece.

References Cited UNITED STATES PATENTS 2,029,491 2/1936 Lane 102-5 X 2,258,281 10/1941 Dunajelf 2443.21 X 3,107,617 10/1963 Loeper et al. 102- 61 3,141,411 7/1964 Menke 2443.16

BENJAMIN A. BORCHELT, Primary Examiner. T. H. WEBB, Assistant Examiner.

US3398916A 1966-07-04 1967-06-19 Device for correcting the trajectory of projectiles and the so-equipped projectiles Expired - Lifetime US3398916A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
BE683586 1966-07-04

Publications (1)

Publication Number Publication Date
US3398916A true US3398916A (en) 1968-08-27

Family

ID=3849029

Family Applications (1)

Application Number Title Priority Date Filing Date
US3398916A Expired - Lifetime US3398916A (en) 1966-07-04 1967-06-19 Device for correcting the trajectory of projectiles and the so-equipped projectiles

Country Status (6)

Country Link
US (1) US3398916A (en)
BE (1) BE683586A (en)
DE (1) DE1578139B1 (en)
ES (1) ES342471A1 (en)
GB (1) GB1193304A (en)
NL (1) NL6708669A (en)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2091901A2 (en) * 1970-04-10 1971-01-21 Etu Realisa Electronique
FR2167608A1 (en) * 1972-01-03 1973-08-24 Ship Systems Inc
US4160415A (en) * 1978-05-05 1979-07-10 The United States Of America As Represented By The Secretary Of The Army Target activated projectile
US4374495A (en) * 1977-09-17 1983-02-22 Thomanek Franz R Warhead for antitank missiles featuring a shaped charge
WO1983003894A1 (en) * 1982-04-21 1983-11-10 Hughes Aircraft Company Terminally guided weapon delivery system
DE3911576A1 (en) * 1989-04-08 1990-10-11 Rheinmetall Gmbh Fluegelstabilisiertes basement
US5261629A (en) * 1989-04-08 1993-11-16 Rheinmetall Gmbh Fin stabilized projectile
US5880396A (en) * 1992-03-27 1999-03-09 Zacharias; Athanassios Process for guiding a flying object and flying objects
WO2000052414A1 (en) * 1999-03-03 2000-09-08 Linick James M Impulse motor to improve trajectory correctable munitions
WO2001090682A1 (en) * 2000-05-25 2001-11-29 Metal Storm Limited Directional control of missiles
US6502785B1 (en) * 1999-11-17 2003-01-07 Lockheed Martin Corporation Three axis flap control system
US6722609B2 (en) * 1998-02-13 2004-04-20 James M. Linick Impulse motor and apparatus to improve trajectory correctable munitions including cannon launched munitions, glide bombs, missiles, rockets and the like
US20050269456A1 (en) * 2003-08-29 2005-12-08 Smiths Aerospace, Inc. Stabilization of a drogue body
US20060226293A1 (en) * 2005-02-25 2006-10-12 Smiths Aerospace Llc Optical tracking system for refueling
US7377468B2 (en) * 2003-08-29 2008-05-27 Smiths Aerospace Llc Active stabilization of a refueling drogue
US8084725B1 (en) * 2008-05-01 2011-12-27 Raytheon Company Methods and apparatus for fast action impulse thruster
RU2443968C2 (en) * 2009-03-19 2012-02-27 Николай Евгеньевич Староверов Anti-helicopter and anti-stealth missile

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2809281C2 (en) * 1978-03-03 1984-01-05 Emile Jean Versailles Fr Stauff
USRE32094E (en) * 1979-11-09 1986-03-25 Avco Corporation Overflying munitions device and system
GB2370342B (en) * 1981-11-05 2002-11-20 Emi Ltd Terminally - corrected sub-munitions
GB2251834B (en) * 1983-02-22 1992-12-16 George Alexander Tarrant Guided missiles
DE3345529C1 (en) * 1983-12-16 1999-09-02 Diehl Stiftung & Co Seeker ammunition arranged before their warhead insert sensor transducer
GB2250804B (en) * 1990-11-07 1994-06-01 Colebrand Ltd Protective device for a sensing head

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2029491A (en) * 1934-08-25 1936-02-04 Technicraft Engineering Corp Gun type formation tester
US2258281A (en) * 1938-05-20 1941-10-07 Commercial Ingredients Corp Aerial torpedo
US3107617A (en) * 1962-04-11 1963-10-22 William F Loeper Ring decoy launching mechanism
US3141411A (en) * 1957-06-19 1964-07-21 Eltro G M B H & Co Ges Fur Str Target finder for missiles

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL2171C (en) * 1914-04-18

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2029491A (en) * 1934-08-25 1936-02-04 Technicraft Engineering Corp Gun type formation tester
US2258281A (en) * 1938-05-20 1941-10-07 Commercial Ingredients Corp Aerial torpedo
US3141411A (en) * 1957-06-19 1964-07-21 Eltro G M B H & Co Ges Fur Str Target finder for missiles
US3107617A (en) * 1962-04-11 1963-10-22 William F Loeper Ring decoy launching mechanism

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2091901A2 (en) * 1970-04-10 1971-01-21 Etu Realisa Electronique
FR2167608A1 (en) * 1972-01-03 1973-08-24 Ship Systems Inc
US4374495A (en) * 1977-09-17 1983-02-22 Thomanek Franz R Warhead for antitank missiles featuring a shaped charge
US4160415A (en) * 1978-05-05 1979-07-10 The United States Of America As Represented By The Secretary Of The Army Target activated projectile
WO1983003894A1 (en) * 1982-04-21 1983-11-10 Hughes Aircraft Company Terminally guided weapon delivery system
DE3911576A1 (en) * 1989-04-08 1990-10-11 Rheinmetall Gmbh Fluegelstabilisiertes basement
US5261629A (en) * 1989-04-08 1993-11-16 Rheinmetall Gmbh Fin stabilized projectile
US5880396A (en) * 1992-03-27 1999-03-09 Zacharias; Athanassios Process for guiding a flying object and flying objects
US6722609B2 (en) * 1998-02-13 2004-04-20 James M. Linick Impulse motor and apparatus to improve trajectory correctable munitions including cannon launched munitions, glide bombs, missiles, rockets and the like
WO2000052414A1 (en) * 1999-03-03 2000-09-08 Linick James M Impulse motor to improve trajectory correctable munitions
US6502785B1 (en) * 1999-11-17 2003-01-07 Lockheed Martin Corporation Three axis flap control system
WO2001090682A1 (en) * 2000-05-25 2001-11-29 Metal Storm Limited Directional control of missiles
US6889935B2 (en) 2000-05-25 2005-05-10 Metal Storm Limited Directional control of missiles
US20050269456A1 (en) * 2003-08-29 2005-12-08 Smiths Aerospace, Inc. Stabilization of a drogue body
US7275718B2 (en) 2003-08-29 2007-10-02 Smiths Aerospace Llc Active control of a drogue body
US7377468B2 (en) * 2003-08-29 2008-05-27 Smiths Aerospace Llc Active stabilization of a refueling drogue
US20060226293A1 (en) * 2005-02-25 2006-10-12 Smiths Aerospace Llc Optical tracking system for refueling
US20080067290A1 (en) * 2005-02-25 2008-03-20 Mickley Joseph G Optical tracking system for airborne objects
US20080075467A1 (en) * 2005-02-25 2008-03-27 Smiths Aerospace Llc Optical tracking system for airborne objects
US7681839B2 (en) 2005-02-25 2010-03-23 Smiths Aerospace Llc Optical tracking system for refueling
US7686252B2 (en) * 2005-02-25 2010-03-30 Smiths Aerospace, Llc Optical tracking system for airborne objects
US20100163679A1 (en) * 2005-02-25 2010-07-01 Mickley Joseph G Optical tracking system for airborne objects
US8104716B2 (en) 2005-02-25 2012-01-31 Ge Aviation Systems Llc Optical tracking system for airborne objects
US8084725B1 (en) * 2008-05-01 2011-12-27 Raytheon Company Methods and apparatus for fast action impulse thruster
RU2443968C2 (en) * 2009-03-19 2012-02-27 Николай Евгеньевич Староверов Anti-helicopter and anti-stealth missile

Also Published As

Publication number Publication date Type
DE1578139B1 (en) 1971-12-23 application
ES342471A1 (en) 1968-07-16 application
GB1193304A (en) 1970-05-28 application
BE683586A (en) 1966-12-16 grant
NL6708669A (en) 1968-01-05 application

Similar Documents

Publication Publication Date Title
US4063512A (en) Armor penetrating projectile
US3903804A (en) Rocket-propelled cluster weapon
US4142696A (en) Guidance devices
US3447463A (en) Dual ignition explosive arrangement
US4183302A (en) Sequential burst system
US3565009A (en) Aimed quadrant warhead
US3796159A (en) Explosive fisheye lens warhead
US4568040A (en) Terminal guidance method and a guided missile operating according to this method
US3610096A (en) Spin and fin stabilized rocket
US4517897A (en) Small arms projectile
US4246472A (en) Controlled store separation system
US3318033A (en) Grenade launching arrangement
Shaw Fighter Combat
US6044765A (en) Method for increasing the probability of impact when combating airborne targets, and a weapon designed in accordance with this method
US3738270A (en) Homing depth bomb for searching for an underwater target
US5816531A (en) Range correction module for a spin stabilized projectile
US3902424A (en) Projectile
US3877383A (en) Munition
US6488233B1 (en) Laser propelled vehicle
US6135387A (en) Method for autonomous guidance of a spin-stabilized artillery projectile and autonomously guided artillery projectile for realizing this method
US20070285304A1 (en) Target orbit modification via gas-blast
US4899956A (en) Self-contained supplemental guidance module for projectile weapons
US3843076A (en) Projectile trajectory correction system
US6565036B1 (en) Technique for improving accuracy of high speed projectiles
US4448106A (en) Method of identifying hard targets